US8956109B2 - Fairing device for nacelle of an aircraft propulsion power unit - Google Patents

Fairing device for nacelle of an aircraft propulsion power unit Download PDF

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Publication number
US8956109B2
US8956109B2 US12/999,093 US99909309A US8956109B2 US 8956109 B2 US8956109 B2 US 8956109B2 US 99909309 A US99909309 A US 99909309A US 8956109 B2 US8956109 B2 US 8956109B2
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cowl
power unit
pylon
propulsion power
lower half
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US12/999,093
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US20110091317A1 (en
Inventor
Sebastien Regard
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Safran Aircraft Engines SAS
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SNECMA SAS
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Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CHANGE OF NAME (SEE DOCUMENT FOR DETAILS). Assignors: SNECMA
Assigned to SAFRAN AIRCRAFT ENGINES reassignment SAFRAN AIRCRAFT ENGINES CORRECTIVE ASSIGNMENT TO CORRECT THE COVER SHEET TO REMOVE APPLICATION NOS. 10250419, 10786507, 10786409, 12416418, 12531115, 12996294, 12094637 12416422 PREVIOUSLY RECORDED ON REEL 046479 FRAME 0807. ASSIGNOR(S) HEREBY CONFIRMS THE CHANGE OF NAME. Assignors: SNECMA
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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D29/00—Power-plant nacelles, fairings, or cowlings
    • B64D29/08—Inspection panels for power plants

Definitions

  • the invention relates to the field of propulsion power units mounted on the fuselage of an aircraft and, in particular, to the fairing devices that envelop gas turbine engines.
  • a propulsion power unit generally comprises a gas turbine engine, a nacelle surrounding the engine, and a nacelle support structure.
  • the nacelle comprises, in the direction in which the gases flow, an air intake structure and at least one fairing device.
  • the propulsion power units are generally mounted at the rear of the fuselage of an aircraft, toward the top.
  • the support structure also known as a pylon, is fixed by a first end to the nacelle.
  • the second end of the pylon is fixed from a rear location on the aircraft fuselage.
  • the fairing device of the nacelle often comprises two opening cowls, an upper cowl and a lower cowl, as described in U.S. Pat. No. 4,585,189. These two opening cowls are mounted on the pylon in such a way that they can pivot about a longitudinal axis of articulation parallel to the engine axis via a pivot system situated where the pylon meets the nacelle.
  • cowls do not encompass the volume formed by the pylon itself.
  • Another technology involves positioning additional cowls for the pylon, which can pivot about a lateral axis of articulation perpendicular to the engine axis via a pivot system, situated at the boundary between the region housing the equipment and the region that contains no equipment. This technology makes maintenance easier by reducing the time taken to gain access, but does have the disadvantage of being more cumbersome and complicated to implement.
  • one subject of the invention is a fairing device for a propulsion power unit comprising a gas turbine engine, a nacelle, of which said fairing device forms a part, and which surrounds the engine, and a support structure known as a pylon for securing to a fuselage of an aircraft, said pylon running in a substantially horizontal plane of symmetry containing the longitudinal axis of the propulsion power unit, and comprising a central compartment open from the top and from the bottom, and designed to house equipment, said pylon being intended to be attached to the fuselage by a distal edge running parallel to the longitudinal axis of the propulsion power unit, the fairing device consisting of at least an upper half-cowl and a lower half-cowl which are substantially symmetric with respect to said plane of symmetry and can be locked together, in the closed position, at their meeting point by a locking means. At least one of said upper and lower half-cowls is mounted so that it can pivot individually on said distal edge of the p
  • the upper half-cowl may comprise a substantially planar first part via which it is pivot-mounted on the distal lateral edge of the pylon and intended to close off the top of the central compartment of the pylon and a second part of semi-cylindrical shape belonging to the nacelle.
  • said second part of the upper half-cowl is formed of at least two portions articulated to one another about an axis running parallel to the longitudinal axis of the propulsion power unit, a first of said portions being made as one piece with said first part of the upper half-cowl.
  • the fairing device for a propulsion power unit comprises at least one holding means for keeping the upper half-cowl in the open position.
  • Said holding means may be an arm pivot-mounted via a first end on said first part of the upper half-cowl and a second end of which is able to come to rest against the pylon so as to immobilize the upper half-cowl in the open position.
  • the center of gravity of the second portion of the upper half-cowl lies in a vertical plane passing through the first end of said holding arm.
  • the lower half-cowl may comprise a substantially planar first part via which it is pivot-mounted on the distal lateral edge of the pylon and intended to close off the underside of the central compartment of the pylon and a second part of semi-cylindrical shape belonging to the nacelle.
  • said second part of the lower half-cowl is formed of at least two portions articulated to one another about an axis running parallel to the longitudinal axis of the propulsion power unit, a first of said portions being made as one piece with said first part of the lower half-cowl.
  • the fairing device for a propulsion power unit comprises at least one holding means for keeping the lower half-cowl in the open position.
  • Said holding means may be an arm pivot-mounted via a first end on said first part of the lower half-cowl and a second end of which is able to catch on the pylon so as to immobilize the lower half-cowl in the open position.
  • the center of gravity of the second portion of the lower half-cowl lies in a vertical plane passing through the first end of said holding arm.
  • FIG. 1 is a perspective view of a propulsion power unit attached to the fuselage of an aircraft and equipped with a fairing device according to the invention
  • FIG. 2 is a front view of the propulsion power unit of FIG. 1 ;
  • FIG. 3 is a view similar to FIG. 2 , of a propulsion power unit equipped with another fairing device according to the invention.
  • FIGS. 1 and 2 are respectively perspective and front views of a propulsion power unit 1 fixed to a fuselage 15 of an aircraft, equipped with a fairing device in the open position, according to the invention.
  • the propulsion power unit 1 comprises a gas turbine engine 4 , a nacelle of which the fairing device forms part and which surrounds the engine 4 , and a support structure 7 known as a pylon.
  • the nacelle of the propulsion power unit 1 comprises, in the direction in which the air flows, an air intake structure 12 , the fairing device, and a thrust reverser 13 .
  • the pylon 7 runs in a substantially horizontal plane of symmetry containing the longitudinal axis X of the propulsion power unit and comprises a central compartment 7 b open at the top and at the bottom, and designed to house equipment, not depicted.
  • the pylon 7 is attached to the fuselage 15 by a distal edge 7 d running parallel to the longitudinal axis of the propulsion power unit 1 , the proximal edge 7 e being attached to the nacelle.
  • the fairing device consists of an upper half-cowl 2 and of a lower half-cowl 3 which are substantially symmetric with respect to said plane of symmetry containing the longitudinal axis X.
  • the half-cowl 2 comprises a substantially planar first part 21 via which it is pivot-mounted, using a pivot device 5 , fixed to a first end 21 a , to the distal lateral edge 7 d of the pylon 7 and intended to close off the top of the central compartment 7 b , and a second part 22 of semi-cylindrical shape, fixed by a first end to a second end 21 b , and intended to complete the upper part of the nacelle.
  • the half-cowl 3 comprises a substantially planar first part 31 via which it is pivot-mounted, using a pivot device 6 , by a first end 31 a to the distal lateral edge 7 d of the pylon 7 and intended to close off the underside of the central compartment 7 b , and a second part 32 , of semi-cylindrical shape, fixed by a first end to a second end 31 b and intended to complete the lower part of the nacelle.
  • the pylon 7 comprises three volumes, denoted 7 a , 7 b and 7 c in the direction in which the gases flow.
  • a volume 7 a of aerodynamic shape, contains no equipment.
  • the volume 7 b of parallelepipedal shape, is accessible and contains equipment, not depicted.
  • a volume 7 c situated at the rear contains no equipment.
  • the three axes, axial X, radial Y and tangential Z situate the axes of the propulsion power unit 1 .
  • the line A is contained in a plane substantially corresponding to the surface of the first part 21 of the half-cowl 2 .
  • the line B is contained in a plane substantially corresponding to the surface of the first part 31 of the half-cowl 3 .
  • Holding arms 9 a and 9 b are fixed respectively to a first end 9 a ′ and 9 b ′ under the second end 21 b of the first part 21 of the half-cowl 2 and under the second end 31 b of the first part 31 of the half-cowl 3 , via rotation devices 14 a and 14 b . These holding arms 9 a and 9 b allow the respective half-cowls 2 and 3 to be kept in the open position.
  • the respective holding arms 9 a and 9 b are retracted and immobilized, in the furled position, by rotation devices 14 a and 14 b under the first parts 21 and 31 of the half-cowls 2 and 3 .
  • the holding arms 9 a and 9 b are fixed, on the one hand, by the rotation devices 14 a and 14 b and, on the other hand, by their end 9 a ′′ and 9 b ′′ at the proximal edge 7 e of the pylon 7 .
  • an angle formed by the line A and the radial engine axis Y is preferably greater than 55°.
  • an angle formed by the line B and the radial engine axis Y, denoted ⁇ is also preferably greater than 55°.
  • the two half-cowls 2 and 3 are locked together in the closed position at their meeting point by a catch 8 a placed on a second end of the part 22 of the upper half-cowl 2 and 8 b placed on a second end of the part 32 of the lower half-cowl 3 .
  • the upper 2 and lower 3 half-cowls are mounted so that they can pivot individually on the distal edge 7 d of the pylon 7 so that when they are in the open position they provide access both to the engine 4 and to the central compartment 7 b of the pylon 7 .
  • the upper half-cowl 2 comprises the first part 21 , the second part 22 being produced in two portions.
  • a first portion 221 of partially semi-cylindrical shape is fixed to the second end 21 b of the first part 21 .
  • a hinge 10 is fixed to the second end of the first portion 221 .
  • the second portion 222 is also of partially semi-cylindrical shape.
  • a first end of the second portion 222 is fixed to the hinge 10 , thus making it possible, in the closed position, to complete the upper part of the nacelle.
  • the catch 8 a is fixed to a second end of the portion 222 .
  • the lower half-cowl 3 comprises a first part 31 , the second part 32 being produced in two portions.
  • a first portion 321 of partially semi-cylindrical shape, is fixed to the second end 31 b of the first part 31 .
  • a hinge 11 is fixed to the second end of the first portion 321 .
  • the second portion 322 is also of partially semi-cylindrical shape.
  • a first end of the second portion 322 is fixed to the hinge 11 , thus making it possible, in the closed position, to complete the lower part of the nacelle.
  • the catch 8 b is fixed to a second end of the portion 322 .
  • the portions 221 and 222 have substantially identical dimensions given the position of the hinge 10 . Bearing in mind the length of the holding arm 9 a , when the upper half-cowl 2 is open, the center of gravity of the second portion 222 lies on a vertical passing through the rotation device 14 a . With this configuration, the second portion 222 fixes itself along the first portion 221 under its own weight.
  • the dimension of the first portion 321 is substantially twice that of the second portion 322 , given the position of the hinge 11 .
  • the center of gravity of the second portion 322 is situated on a vertical passing through the rotation device 14 b .
  • the second portion 322 will fix itself, under its own weight, toward the inside of the semi-cylindrical shape of the first portion 321 .
  • the hinges 10 and 11 could be located differently, which would entail different respective dimensions for the portions 221 and 222 on the one hand, and 321 and 322 on the other.
  • the drive for opening the half-cowls 2 and 3 may be provided manually or automatically, it being possible for each half-cowl to be opened independently of the other, or not.
  • the rotation devices 14 a and 14 b could be situated at the proximal end 7 e of the pylon 7 .
  • a second end 9 a ′′ and 9 b ′′ of the holding arms 9 a and 9 b respectively is fixed, when the fairing device is in the open position, in a region configured for this immobilization, under the junction between the parts 210 and 221 of the half-cowl 2 and under the junction of the parts 310 and 321 of the half-cowl 3 respectively.
  • the holding arms 9 a and 9 b are retracted and immobilized, furled, by the hinges 14 a and 14 b under the first parts 21 and 22 of the half-cowls 2 and 3 respectively.
  • the holding arms 9 a and 9 b could also be brought back on each operation of opening the fairing device.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Wind Motors (AREA)
  • Superstructure Of Vehicle (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US12/999,093 2008-06-25 2009-04-10 Fairing device for nacelle of an aircraft propulsion power unit Active 2030-11-27 US8956109B2 (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0803554A FR2933071B1 (fr) 2008-06-25 2008-06-25 Dispositif de capotage de nacelle d'unite de puissance propulsive d'aeronef
FR0803554 2008-06-25
PCT/FR2009/000423 WO2010007218A1 (fr) 2008-06-25 2009-04-10 Dispositif de capotage de nacelle d'unite de puissance propulsive d'aeronef

Publications (2)

Publication Number Publication Date
US20110091317A1 US20110091317A1 (en) 2011-04-21
US8956109B2 true US8956109B2 (en) 2015-02-17

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US12/999,093 Active 2030-11-27 US8956109B2 (en) 2008-06-25 2009-04-10 Fairing device for nacelle of an aircraft propulsion power unit

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US (1) US8956109B2 (pt)
EP (1) EP2303693B1 (pt)
JP (1) JP2011525874A (pt)
CN (1) CN102076564A (pt)
BR (1) BRPI0914324B1 (pt)
CA (1) CA2728700C (pt)
ES (1) ES2395863T3 (pt)
FR (1) FR2933071B1 (pt)
RU (1) RU2494926C2 (pt)
WO (1) WO2010007218A1 (pt)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140334922A1 (en) * 2013-05-13 2014-11-13 Airbus Operations (Sas) Aircraft turbojet nacelle
US20160264249A1 (en) * 2015-03-12 2016-09-15 Rohr, Inc. Track mounted hold open rod
US9783314B2 (en) 2014-07-31 2017-10-10 Airbus Operations S.A.S. Foldable guiding ventilator cover for an aircraft engine assembly
US10093429B2 (en) * 2015-07-07 2018-10-09 Rohr, Inc Latch beam deflection support

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Publication number Priority date Publication date Assignee Title
FR2939100B1 (fr) * 2008-12-01 2010-12-31 Airbus France Ensemble moteur pour aeronef comprenant une structure rigide modulaire de mat d'accrochage
WO2014197029A2 (en) * 2013-03-14 2014-12-11 United Technologies Corporation Latching actuation mechanism for nacelle mounted latching system
FR3009542B1 (fr) * 2013-08-07 2015-08-07 Airbus Operations Sas Assemblage pour aeronef comprenant un panneau d'acces aux articulations d'un capot de nacelle monte pivotant sur un dispositif d'accrochage de moteur d'aeronef
FR3009543B1 (fr) * 2013-08-07 2015-08-07 Airbus Operations Sas Assemblage pour aeronef comprenant un panneau d'acces aux articulations d'un capot de nacelle deplacable par cooperation entre une rampe et un organe d'appui
DE102015206093A1 (de) * 2015-04-02 2016-10-06 Rolls-Royce Deutschland Ltd & Co Kg Triebwerksverkleidung einer Fluggasturbine
FR3036382B1 (fr) 2015-05-21 2017-06-16 Airbus Operations Sas Nacelle d'aeronef comportant au moins un capot monte rotatif autour de l'axe longitudinal de la nacelle
FR3040044B1 (fr) * 2015-08-12 2019-05-31 Safran Aircraft Engines Capot de nacelle comportant un element de maintien en position solidarise a la paroi interne du capot
CN106741974A (zh) * 2016-12-12 2017-05-31 惠阳航空螺旋桨有限责任公司 一种螺旋桨用复合材料整流罩
US10875656B2 (en) 2017-09-15 2020-12-29 Bell Helicopter Textron Inc. Bi-folding engine cowl having a plurality of open positions to provide access
US10875657B2 (en) 2017-09-15 2020-12-29 Bell Helicopter Textron Inc. Hold open j-track locking mechanism for cowling
FR3075176B1 (fr) * 2017-12-18 2020-11-06 Safran Aircraft Engines Ensemble de capot ouvrant et mecanisme de deploiement
FR3079216A1 (fr) * 2018-03-22 2019-09-27 Airbus Operations Carenage avant d'un mat d'aeronef comprenant au moins un panneau articule et aeronef equipe dudit carenage avant
FR3079500A1 (fr) * 2018-03-29 2019-10-04 Airbus Operations Nacelle d'aeronef a capot de soufflante rotatif integrant une trappe d'acces
FR3085351B1 (fr) * 2018-09-04 2021-12-31 Airbus Operations Sas Carenage central d'un mat d'aeronef comprenant au moins un panneau articule et aeronef equipe dudit carenage central
CN110065639A (zh) * 2019-05-09 2019-07-30 西北工业大学 一种用于无人机快卸对开式动力舱罩
CN114728701A (zh) * 2019-11-25 2022-07-08 Mra系统有限责任公司 飞行器发动机机舱整流罩机构
FR3113485B1 (fr) 2020-08-21 2022-10-28 Safran Nacelles Nacelle pour moteur d’aéronef comportant des capots de soufflante asymétriques
US20220136440A1 (en) * 2020-10-30 2022-05-05 Raytheon Technologies Corporation Gas turbine engine mounted above wing and with camber

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FR2862045B1 (fr) * 2003-11-12 2006-05-05 Snecma Moteurs Turboreacteur destine a etre fixe sur le fuselage d'un avion et en particulier sur sa partie arriere

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US4428609A (en) * 1980-09-15 1984-01-31 The Boeing Company Latch for flexibly joining trailing edge access doors on an aircraft engine support pylon
US4585189A (en) * 1984-10-22 1986-04-29 Lockheed Corporation Counterbalanced cowling assembly for a pylon-mounted engine and nacelle therefor
GB2202588A (en) 1987-03-02 1988-09-28 Gen Electric Turbofan engine
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US6227485B1 (en) * 1997-12-03 2001-05-08 Aerospatiale Societe Nationale Industrielle Opening device common to two adjacent aircraft engine nacelle covers
US6220546B1 (en) * 1999-12-29 2001-04-24 The Boeing Company Aircraft engine and associated aircraft engine cowl
FR2830842A1 (fr) 2001-10-11 2003-04-18 Short Brothers Plc Unite de puissance propulsive pour avion
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Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20140334922A1 (en) * 2013-05-13 2014-11-13 Airbus Operations (Sas) Aircraft turbojet nacelle
US9604728B2 (en) * 2013-05-13 2017-03-28 Airbus Operations (S.A.S.) Aircraft turbojet nacelle
US9783314B2 (en) 2014-07-31 2017-10-10 Airbus Operations S.A.S. Foldable guiding ventilator cover for an aircraft engine assembly
US20160264249A1 (en) * 2015-03-12 2016-09-15 Rohr, Inc. Track mounted hold open rod
US10081434B2 (en) * 2015-03-12 2018-09-25 Rohr, Inc. Track mounted hold open rod
US10093429B2 (en) * 2015-07-07 2018-10-09 Rohr, Inc Latch beam deflection support

Also Published As

Publication number Publication date
WO2010007218A1 (fr) 2010-01-21
FR2933071A1 (fr) 2010-01-01
US20110091317A1 (en) 2011-04-21
CA2728700A1 (fr) 2010-01-21
CN102076564A (zh) 2011-05-25
RU2011102573A (ru) 2012-07-27
EP2303693B1 (fr) 2012-10-31
JP2011525874A (ja) 2011-09-29
RU2494926C2 (ru) 2013-10-10
BRPI0914324A2 (pt) 2015-10-13
CA2728700C (fr) 2015-10-27
FR2933071B1 (fr) 2010-06-11
EP2303693A1 (fr) 2011-04-06
BRPI0914324B1 (pt) 2019-12-03
ES2395863T3 (es) 2013-02-15

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